MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.54 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh24-il-1000000.txt Download as CSV file: xf-mh24-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4672 0.09137 0.08979 -0.0319 1.0000 0.0073
-9.250 -0.4785 0.08880 0.08725 -0.0302 1.0000 0.0073
-9.000 -0.4868 0.08550 0.08397 -0.0302 0.9998 0.0073
-8.750 -0.4815 0.07976 0.07825 -0.0359 0.9986 0.0073
-8.500 -0.4776 0.07265 0.07114 -0.0457 0.9963 0.0073
-8.250 -0.4758 0.06603 0.06445 -0.0529 0.9934 0.0073
-8.000 -0.4748 0.06104 0.05936 -0.0555 0.9895 0.0073
-7.750 -0.4673 0.05572 0.05392 -0.0583 0.9869 0.0073
-7.500 -0.4572 0.05050 0.04853 -0.0605 0.9849 0.0073
-7.250 -0.4444 0.04576 0.04359 -0.0620 0.9833 0.0074
-7.000 -0.4458 0.03738 0.03481 -0.0622 0.9806 0.0076
-6.750 -0.4505 0.03142 0.02845 -0.0593 0.9756 0.0081
-6.500 -0.4352 0.02845 0.02525 -0.0586 0.9733 0.0086
-4.000 -0.2156 0.01198 0.00679 -0.0471 0.9488 0.0078
-3.750 -0.1948 0.01059 0.00530 -0.0453 0.9458 0.0065
-3.500 -0.1731 0.00973 0.00431 -0.0437 0.9431 0.0060
-3.250 -0.1512 0.00921 0.00368 -0.0423 0.9395 0.0057
-3.000 -0.1280 0.00880 0.00316 -0.0411 0.9357 0.0056
-2.750 -0.1030 0.00852 0.00280 -0.0403 0.9326 0.0056
-2.500 -0.0770 0.00829 0.00249 -0.0396 0.9299 0.0062
-2.250 -0.0533 0.00797 0.00226 -0.0387 0.9261 0.0379
-2.000 -0.0362 0.00701 0.00202 -0.0368 0.9214 0.2371
-1.750 -0.0186 0.00612 0.00182 -0.0351 0.9176 0.4392
-1.500 -0.0097 0.00502 0.00167 -0.0313 0.9125 0.7076
-1.250 0.0048 0.00458 0.00182 -0.0278 0.9076 0.8803
-1.000 0.0314 0.00455 0.00177 -0.0272 0.9039 0.8965
-0.750 0.0571 0.00455 0.00177 -0.0266 0.8992 0.9078
-0.500 0.0828 0.00454 0.00173 -0.0259 0.8938 0.9170
-0.250 0.1099 0.00455 0.00170 -0.0255 0.8893 0.9242
0.000 0.1347 0.00458 0.00174 -0.0246 0.8824 0.9317
0.250 0.1606 0.00463 0.00177 -0.0238 0.8762 0.9398
0.500 0.1869 0.00468 0.00182 -0.0232 0.8670 0.9452
0.750 0.2154 0.00472 0.00185 -0.0232 0.8565 0.9490
1.000 0.2412 0.00474 0.00183 -0.0226 0.8427 0.9533
1.250 0.2679 0.00477 0.00180 -0.0222 0.8237 0.9568
1.500 0.2998 0.00489 0.00182 -0.0229 0.7941 0.9590
1.750 0.3324 0.00511 0.00189 -0.0239 0.7568 0.9617
2.000 0.3613 0.00537 0.00199 -0.0241 0.7133 0.9652
2.250 0.3827 0.00562 0.00207 -0.0227 0.6706 0.9696
2.500 0.4153 0.00590 0.00216 -0.0239 0.6203 0.9706
2.750 0.4458 0.00620 0.00225 -0.0248 0.5653 0.9716
3.000 0.4749 0.00650 0.00237 -0.0254 0.5121 0.9727
3.250 0.5034 0.00680 0.00249 -0.0259 0.4607 0.9741
3.500 0.5307 0.00712 0.00261 -0.0261 0.4094 0.9758
3.750 0.5559 0.00746 0.00275 -0.0259 0.3574 0.9779
4.000 0.5773 0.00777 0.00292 -0.0248 0.3128 0.9807
4.250 0.6022 0.00808 0.00306 -0.0245 0.2707 0.9824
4.500 0.6305 0.00850 0.00324 -0.0251 0.2148 0.9832
4.750 0.6589 0.00887 0.00343 -0.0257 0.1708 0.9841
5.000 0.6874 0.00925 0.00365 -0.0263 0.1341 0.9851
5.250 0.7148 0.00968 0.00390 -0.0267 0.0963 0.9862
5.500 0.7415 0.01010 0.00420 -0.0270 0.0652 0.9875
5.750 0.7685 0.01050 0.00449 -0.0272 0.0438 0.9889
6.000 0.7953 0.01084 0.00478 -0.0274 0.0310 0.9903
6.250 0.8208 0.01121 0.00512 -0.0273 0.0207 0.9919
6.500 0.8451 0.01159 0.00546 -0.0269 0.0136 0.9934
6.750 0.8724 0.01192 0.00579 -0.0272 0.0100 0.9943
7.000 0.8988 0.01266 0.00656 -0.0273 0.0032 0.9953
7.250 0.9262 0.01327 0.00728 -0.0275 0.0027 0.9965
7.500 0.9525 0.01397 0.00811 -0.0276 0.0026 0.9977
7.750 0.9774 0.01483 0.00911 -0.0274 0.0025 0.9990
8.000 0.9993 0.01589 0.01037 -0.0266 0.0024 1.0000
8.250 1.0071 0.01683 0.01147 -0.0229 0.0024 1.0000
8.500 1.0134 0.01782 0.01260 -0.0189 0.0025 1.0000
8.750 1.0164 0.01909 0.01404 -0.0143 0.0025 1.0000
9.000 1.0190 0.02041 0.01555 -0.0096 0.0025 1.0000
9.250 1.0189 0.02221 0.01758 -0.0046 0.0026 1.0000
9.500 1.0188 0.02431 0.01993 0.0002 0.0027 1.0000
9.750 1.0159 0.02694 0.02286 0.0052 0.0028 1.0000
10.000 1.0132 0.02933 0.02552 0.0097 0.0029 1.0000
10.250 1.0006 0.03205 0.02852 0.0156 0.0030 1.0000
10.500 0.9687 0.03652 0.03337 0.0231 0.0032 1.0000
13.000 0.7196 0.08622 0.08464 0.0126 0.0032 1.0000
13.250 0.7081 0.09423 0.09271 0.0085 0.0032 1.0000
13.500 0.6929 0.10306 0.10159 0.0043 0.0031 1.0000
13.750 0.6720 0.11307 0.11165 -0.0003 0.0032 1.0000
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Polar data table (+)
Polar graphs
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